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A new aerodynamic design method has been proposed for supersonic or transonic axial flow compressors.The aim of this design method is to largely increase the stage load efficiently with boundary layer suction (BLS) used only in the stator,which can reduce the difficult of the air bleed system design in the rotating part and to improve the reliability of the stage.Compared with the conventional supersonic shock-in type rotor,the rotor designed by this method can further increase the turning of the flow to enhance the stage work; while compared with the traditional supersonic impulse rotor,it can reduce the exit absolute Mach number of the rotor to relieve the design difficult of the downstream stator.But when the turning of the flow in the rotor is largely increased,the entrance Mach number of the stator usually increases inevitably,so BLS is used in the stator to solve its internal flow problems.Based on numerical simulation,a verification stage has been designed to demonstrate the feasibility of this method.From the three-dimensional viscous numerical results,a stage with total pressure ratio 2.55 and efficiency 88.1% has been attained at tip tangential speed 370m/s.And the total bleed mass flow in the stator is around 6.3% of the inlet.